Frequency-Domain Rotor Mode Decomposition for Vibration Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Rotorcrafts face challenges in managing complex flight dynamics due to tightly coupled flight parameters, which can lead to instability and increased pilot workload, especially as they transition between different flight regimes like cruising and hovering.
Innovation Solution
A system and method that utilize mode sensors and a mode analysis system to decompose sensor data into fundamental modes of structural elements, allowing a flight control computer to adjust control inputs based on these modes, thereby improving stability and reducing vibration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If traditional flight control systems are used to manage rotorcraft flight dynamics, then the system structure is simple, but the flight stability deteriorates due to tightly coupled flight parameters
Solution Approach 1:
The patent segments the complex flight control system into multiple independent mode controllers, each responsible for a specific structural mode (blade flapping, lead-lag, fuselage bending, etc.). This segmentation allows the tightly coupled flight parameters to be decoupled and controlled independently, improving flight stability while maintaining manageable system complexity through modular architecture.
Solution Approach 2:
The system transforms the control approach by changing from direct control of flight parameters to control of structural modes. By identifying and controlling the fundamental structural modes of the rotorcraft, the system achieves better stability without proportionally increasing complexity, as the mode-based control framework provides a systematic way to handle parameter coupling.
2Measurement precision
If mode decomposition system is implemented to analyze structural modes, then the flight control precision is improved, but the computational complexity increases
Solution Approach 1:
The system performs preliminary identification of structural modes and their characteristics before actual flight control operations. By pre-characterizing the structural modes and preparing the decomposition framework in advance, the system reduces real-time computational burden while maintaining high analysis precision during flight control.
Solution Approach 2:
The mode decomposition system implements continuous feedback by monitoring structural responses and adjusting control inputs based on identified mode characteristics. This feedback mechanism maintains high measurement precision while managing computational complexity through iterative refinement rather than exhaustive real-time calculation.
3Measurement precision
If multiple mode sensors are deployed to capture structural vibrations, then the measurement accuracy is improved, but the system complexity and cost increase
Solution Approach 1:
The patent employs accelerometers that serve multiple functions: they detect structural vibrations for mode identification, provide flight attitude information, and contribute to overall flight control. This multi-functionality allows the system to achieve high measurement accuracy for structural modes without proportionally increasing sensor system complexity, as the same sensors support multiple measurement objectives.
Data Source
AI summary
A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.